Solid seal with cooling pathways

ABSTRACT

The present application provides a seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine. The seal may include a first surface facing the high pressure cooling air flow, a second surface with a second surface air plenum facing the hot gas path, and a number of cooling pathways extending from the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough.

TECHNICAL FIELD

The present application and resultant patent relate generally to gasturbine engines and more particularly relate to solid seals and the likehaving cooling pathways extending therethrough.

BACKGROUND OF THE INVENTION

Generally described, turbo-machinery such as gas turbine engines and thelike include a main gas flow path extending therethrough. Gas leakage,either out of the gas flow path or into the gas flow path, may loweroverall gas turbine efficiency, increase fuel costs, and possiblyincrease emission levels. Secondary flows also may be used within thegas turbine engine to cool the various heated components. Specifically,cooling air may be extracted from the later stages of the compressor foruse in cooling the heated components and for purging gaps and cavitiesbetween adjacent components. For example, seals may be placed betweenturbine components such as stators and the like. These locations,however, may face very high temperatures and velocities that may lead toheavy oxidation and even seal failure. This potential damage may bemitigated somewhat by providing purge air to the gap with the sealtherein. This purge air, however, may be a largely inefficient use ofthe cooling air.

There is thus a desire for improved solid seal for use between statorcomponents and other components in a heavy duty gas turbine engine. Sucha solid seal may be cooled with less flow than is generally necessary topurge the gap therein for higher overall efficiency and with increasedcomponent lifetime.

SUMMARY OF THE INVENTION

The present application and the resultant patent thus provide a seal foruse between components facing a high pressure cooling air flow and a hotgas path in a gas turbine engine and the like. The seal may include afirst surface facing the high pressure cooling air flow, a secondsurface having a second surface air plenum facing the hot gas path, anda number of cooling pathways extending from the first surface to thesecond surface air plenum of the second surface for the high pressurecooling air flow to pass therethrough.

The present application and the resultant patent further provide amethod of cooling a seal positioned between components in a gas turbineengine. The method may include the steps of flowing high pressurecooling air about a first surface of the seal, drawing the high pressurecooling air through a number of cooling pathways in the seal, anddrawing the high pressure cooling air through an air plenum about asecond surface of the seal towards a hot gas path. The method mayinclude the further step of cooling the components with the highpressure cooling air passing through the air plenum.

The present application and the resultant patent further provide a solidseal for use between components facing a high pressure cooling air flowand a hot gas path in a gas turbine engine. The solid seal may include afirst surface with a first surface air plenum facing the high pressurecooling air flow, a second surface with a second surface air plenumfacing the hot gas path, and a number of cooling pathways extending fromthe first surface air plenum of the first surface to the second surfaceair plenum of the second surface for the high pressure cooling air flowto pass therethrough.

These and other features and improvements of the present application andthe resultant patent will become apparent to one of ordinary skill inthe art upon review of the following detailed description when taken inconjunction with the several drawings and the appended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic view of a gas turbine engine showing a compressor,a combustor, and a turbine.

FIG. 2 is a partial side view of a turbine showing a number ofcomponents positioned along a hot gas path.

FIG. 3 is a side cross-sectional view of a known seal positioned betweenadjacent turbine components.

FIG. 4 is a perspective view of a solid seal as may be described hereinwith a number of cooling pathways extending therethrough.

FIG. 5 is a side cross-sectional view of the solid seal of FIG. 4 withthe cooling pathways extending therethrough.

DETAILED DESCRIPTION

Referring now to the drawings, in which like numerals refer to likeelements throughout the several views, FIG. 1 shows a schematic view ofgas turbine engine 10 as may be used herein. The gas turbine engine 10may include a compressor 15. The compressor 15 compresses an incomingflow of air 20. The compressor 15 delivers the compressed flow of air 20to a combustor 25. The combustor 25 mixes the compressed flow of air 20with a pressurized flow of fuel 30 and ignites the mixture to create aflow of combustion gases 35. Although only a single combustor 25 isshown, the gas turbine engine 10 may include any number of combustors25. The flow of combustion gases 35 is in turn delivered to a turbine40. The flow of combustion gases 35 drives the turbine 40 so as toproduce mechanical work. The mechanical work produced in the turbine 40drives the compressor 15 via a shaft 45 and an external load 50 such asan electrical generator and the like.

The gas turbine engine 10 may use natural gas, various types of syngas,and/or other types of fuels. The gas turbine engine 10 may be any one ofa number of different gas turbine engines offered by General ElectricCompany of Schenectady, New York, including, but not limited to, thosesuch as a 7 or a 9 series heavy duty gas turbine engine and the like.The gas turbine engine 10 may have different configurations and may useother types of components. Other types of gas turbine engines also maybe used herein. Multiple gas turbine engines, other types of turbines,and other types of power generation equipment also may be used hereintogether.

FIG. 2 shows a portion of the turbine 40. Generally described, theturbine 40 may include a first stage nozzle 55, a first stage bucket 60,and a first stage shroud 62 of a first stage 65. Also shown is a secondstage nozzle 70 of a second stage 75. Any number of stages may be usedherein. The nozzles 55, 70 may be positioned on a diaphragm 80. Anynumber of nozzles 70 and diaphragms 80 may be positionedcircumferentially about an axis 85. A seal 90 may be positioned betweeneach pair of adjacent shrouds 62, diaphragms 80, or other turbinecomponents. The seal 90 may be used between adjacent turbine componentsso as to prevent the leakage of the cooling air flows 20 from thecompressor 15 or elsewhere therethrough. As described above, the seals90 may have many different configurations. Other types of sealingmechanisms also may be used. Other components and other configurationsmay be used herein.

FIG. 3 shows an example of the seal 90 positioned between adjacentturbine components, a first component 92 and a second component 94. Thecomponents 92, 94 may be adjacent turbine components such as statorcomponents and the like. The turbine components 92, 94 may define a sealslot 95 therebetween. The seal 90 may be a solid material seal althoughother types of seals may be used. Any number of the seals 90 may be usedherein. The seals 90 may prevent or reduce leakage of a flow of highpressure cooling air 96 between the components 92, 94 into the lowerpressure hot gas path 98.

FIG. 4 shows an example of a seal 100 as may be described herein. Theseal 100 may have a top surface 110, a bottom surface 120 (a slashface), a first side 130, an opposed second side 140, a first end 150,and an opposed second end 160. (The terms “bottom,” “top,” “side,”“end,” “first,” “second,” and the like are used for the purposes ofrelative orientation only and not as an absolute position.) The seal 100may be a solid seal 170. Alternatively, the seal 100 may have a numberof layers of material therein. The seal 100 may be made out of a hightemperature material such as stainless steel, nickel-based alloys, andthe like. Other types of materials also may be used herein. The seal 100may have any size, shape, or configuration.

As is shown in cross-section in FIG. 5, the seal 100 may have asubstantial “I-beam” like shape 180. Specifically, the seal 100 mayinclude a first plenum 190 defined by a first peripheral lip 200 aboutthe top surface 110 thereof and a second plenum 210 defined by a secondperipheral lip 220 about the bottom surface 120 thereof. The plenums190, 210 thus may be recessed areas within the top surface 110 and thebottom surface 120 of the seal. The plenums 190, 210 and the peripherallips 200, 220 may have any size, shape, or configuration. Multipleplenums 190, 210 also may be used. The peripheral lips 200, 220 maydefine a first blocked end 230 on the first end 150 and a second blockedend 240 on the second end 160. The blocked ends 220, 240 may have anysize, shape, or configuration. One or more open ends also may be used.Alternatively, the blocked ends 220, 240 may have cooling holes or slotspositioned therein. Other components and other configurations may beused herein.

The seal 100 also may include a number of cooling pathways 250 extendingtherethrough from the first plenum 190 to the second plenum 210. Anynumber of the cooling pathways 250 may be used herein. The coolingpathways 250 may have any suitable size, shape, or configuration.Further, the cooling pathways 250 may extend through the seal 100 at astraight and/or an angled configuration. Any angle or combinations ofangles may be used. The cooling pathways 250 may be formed by drillingor other types of manufacturing techniques. Cooling pathways 250 ofdiffering configurations may be used herein together. Other componentsand other configurations may be used herein.

In use, the seal 100 may be positioned between the first component 92and the second component 94 within the seal slot 95. The top surface 110of the seal 100 may face the high pressure cooling air 96 while thebottom surface 120 may face the lower pressure hot gas path 98. The seal100 may have any number of the cooling pathways 250 extendingtherethrough in any configuration. The seal cooling pathways 250extending into the second plenum 210 also act as impingement holesand/or purge holes for the seal slot 95. Specifically, the pressuredifferential between the high pressure cooling air 96 and the lowerpressure hot gas path 98 draws the high pressure cooling air 96 throughthe cooling pathways 250 and into the second plenum 210 about the bottomsurface 120 of the seal 100. The high pressure cooling air 96 thusenhances heat transfer through the seal 100 and impinges upon/purges theseal slot 95 via the impingement holes.

The cooling pathways 250 may be positioned strategically near localizedhot spots or uniformly along the length of the seal 100. The coolingpathways 250 may have any prescribed pitch along the length of the seal100. The use of the blocked ends 230, 240 also substantially limits anygap leakage about the ends 150, 160 of the seal 100. The seal 100 andthe cooling pathways 250 therethrough thus provide purging and coolingof the bottom surface 120 or the slash face as well as about the sealingslot 95 in an efficient manner.

Moreover, the seal 100 described herein may provide increased seallifetime, reduced secondary flows, higher overall engine efficiency, anda reduced heat rate. The seal 100 may be original equipment or part of aretro-fit. Different configurations of the seals 100 may be usedtogether herein. The seal 100 also may be applicable for use in othertypes of sealing locations. Specifically, the seal 100 may be usedbetween any two components with a pressure differential therebetween fora flow of cooling air.

It should be apparent that the foregoing relates only to certainembodiments of the present application and the resultant patent.Numerous changes and modifications may be made herein by one of ordinaryskill in the art without departing from the general spirit and scope ofthe invention as defined by the following claims and the equivalentsthereof.

We claim:
 1. A seal for use between components facing a high pressurecooling air flow and a hot gas path in a gas turbine engine, comprising:a first surface facing the high pressure cooling air flow; a secondsurface facing the hot gas path; the second surface comprising a secondsurface air plenum; and a plurality of cooling pathways extending fromthe first surface to the second surface air plenum of the second surfacefor the high pressure cooling air flow to pass therethrough.
 2. The sealof claim 1, wherein the seal comprises a solid seal.
 3. The seal ofclaim 1, wherein the seal comprises a substantial “I” beam-like shape.4. The seal of claim 1, wherein the second surface comprises a secondsurface peripheral lip.
 5. The seal of claim 1, wherein the firstsurface comprises a first surface air plenum.
 6. The seal of claim 1,wherein the first surface comprises a first surface peripheral lip. 7.The seal of claim 1, wherein the first surface comprises a top surfaceand wherein the second surface comprises a bottom surface.
 8. The sealof claim 1, further comprising a first blocked end and a second blockedend.
 9. The seal of claim 1, wherein the plurality of cooling holescomprises a straight configuration.
 10. The seal of claim 1, wherein theplurality of cooling holes comprises an angled configuration.
 11. Theseal of claim 1, wherein the plurality of cooling holes comprises aplurality of impingement holes.
 12. The seal of claim 1, wherein thecomponents comprise a first stator and a second stator
 13. The seal ofclaim 1, wherein the components define a seal slot and wherein the sealslot is cooled via the high pressure cooling air flow from the pluralityof cooling pathways.
 14. A method of cooling a seal positioned betweencomponents in a gas turbine engine, comprising: flowing high pressurecooling air about a first surface of the seal; drawing the high pressurecooling air through a plurality of cooling pathways in the seal; anddrawing the high pressure cooling air through an air plenum about asecond surface of the seal towards a hot gas path.
 15. The method ofclaim 14, further comprising the step of cooling the components with thehigh pressure cooling air leaving the air plenum.
 16. A solid seal foruse between components facing a high pressure cooling air flow and a hotgas path in a gas turbine engine, comprising: a first surface facing thehigh pressure cooling air flow; the first surface comprising a firstsurface air plenum; a second surface facing the hot gas path; the secondsurface comprising a second surface air plenum; and a plurality ofcooling pathways extending from the first surface air plenum of thefirst surface to the second surface air plenum of the second surface forthe high pressure cooling air flow to pass therethrough.
 17. The solidseal of claim 16, wherein the seal comprises a substantial “I” beam-likeshape.
 18. The solid seal of claim 16, wherein the first surfacecomprises a first surface peripheral lip and wherein the second surfacecomprises a second surface peripheral lip.
 19. The solid seal of claim16, further comprising a first blocked end and a second blocked end. 20.The solid seal of claim 16, wherein the plurality of cooling holescomprises a plurality of impingement holes with a straight configurationand/or an angled configuration.